Abstract: A missile flight path of parallel approaching method decided by launching parameters is used as a reference trajectory and the change produced by all kinds of disturbance is treated as deviation. An optimal guidance law of air-to-air missiles attacking in all-direction is obtained by the theory of optimal control. The loop of missile control systems includes the feed back of maneuvering acceleration of target. When targets fly with non-maneuvering, the optimal guidance law is the proportional guidance law with a changeable factor. The numerical computation confirms that the load-factor needed and the terminal error are much smaller than that produced by initial conditions and the same target. Especially when a missile attacks a target in the front of it, the guidance precision is much higher than that of the other guidance law.

Key words: attacking in all-directional, maneuvering target, optimal guidance law